JP6820272B2 - Turbine blade trailing edge with low flow frame channel - Google Patents

Description

The present invention relates to a cooling system for use in the blades of a turbine engine, and more particularly to a trailing edge cooling circuit and a core used to form a trailing edge cooling circuit.

In a gas turbine engine, the compressed air discharged from the compressor section is mixed with the fuel and burned in the combustion section to produce combustion products containing high temperature combustion gas. Combustion gas is sent through hot gas passages in the turbine section. The turbine section has a series of turbine stages. A series of turbine stages typically includes multiple rows of fixed vanes and rotating turbine blades. Turbine blades extract energy from the combustion gas and provide rotation of the turbine rotor to power and provide power to the compressor.

Vane and blade blades are typically exposed to high operating temperatures and are therefore equipped with cooling circuits to remove heat from the blades and extend the life of the vanes and blade components. Some of the compressed air discharged from the compressor section may be diverted to these cooling circuits. Manufacture of blades with one or more cooling circuits typically requires the use of a ceramic core, which provides sufficient structural stability and prevents unzipping of the ceramic core during casting. In order to do so, it has a frame-shaped channel (framing channel) in the inner and outer parts in the radial direction.

According to one aspect of the invention, a core structure for casting gas turbine engine blades is provided. The core structure has a trailing edge section for forming the trailing edge of the gas turbine engine blade, at least part of the trailing edge section defined by a plurality of radial channel elements and axially extending passage elements. It has a plurality of ribbed openings and a low flow framing channel element located adjacent to the radial outer edge of the trailing edge section. The rib-forming openings are arranged in columns aligned in the radial direction, and every other radial rib-forming opening forms a row aligned in the axial direction. The radial outer low flow framed channel element has a plurality of notches extending radially inward from the radial outer edge. Ribbing openings with outer rows aligned in the first axial direction extend radially so that the distal portion of the notch has outer rows aligned in the first axial direction. It overlaps the rib forming opening in the axial direction, and the axial direction is defined between the front edge and the trailing edge of the wing. The notch is radially aligned with the outer row of ribbed openings aligned in the second axial direction. The radial height of the first and / or second axially extending passage elements is greater than the major radial heights of the other axially extending passage elements in the core structure.

In some aspects of the core structure, a ribbing opening with an outer row aligned in the third axial direction is a ribbing opening having an outer row aligned in the second axial direction. It may extend radially so as to axially overlap the ribbed openings having outer rows aligned with. In another embodiment, the radial height H ₁ of the passage element which extends in a first axial direction may also be radial height H ₂ or more passageways elements extending in a second axial, H ₂ is It may be greater than or equal to the major radial height H. In an additional aspect, at least a portion of the radial outer edge between the notches may have a substantially flat region.

In another aspect of the core structure, the trailing edge section may further have a radial inner low flow frame-like channel element located adjacent to the radial inner edge of the trailing edge section. The low flow rate frame-shaped channel element on the inner side in the radial direction may have a plurality of notches extending from the inner edge in the radial direction to the outer side in the radial direction. The inner row of ribbed openings aligned in the first axial direction is radial so that the distal portion of the notch overlaps the ribbed opening with the inner row aligned in the first axial direction in the axial direction. It may be extended to. The notches in the radial inner low flow framing channel may be radially aligned with the inner row of ribbed openings aligned in the second axial direction of the ribbed openings. In certain embodiments, at least a portion of the radial inner edge between the notches may have a substantially flat region.

According to another aspect of the invention, a core structure for forming a cooling configuration on a gas turbine engine blade is provided. The gas turbine engine blade has an outer wall that forms a front edge, a trailing edge, a positive pressure surface, a negative pressure surface, a radial outer tip, and a radial inner end. The core structure has a trailing edge section that forms the trailing edge of the gas turbine engine blade. The trailing edge section has multiple ribbed openings defined by multiple radially extending channel elements and axially extending passage elements, and a radial outer side arranged adjacent to the radial outer edge of the trailing edge section. It has a low flow frame-shaped channel element and a radial inner low flow frame-shaped channel element arranged adjacent to the radial inner edge of the trailing edge section. The rib-forming openings are arranged in columns aligned in the radial direction, and every other radial rib-forming opening forms a row aligned in the axial direction.

The radial outer low flow framed channel element has a plurality of notches extending radially inward from the radial outer edge. Ribbing openings with outer rows aligned in the first axial direction extend radially so that the distal portion of the notch has outer rows aligned in the first axial direction. It overlaps the rib forming opening in the axial direction, and the axial direction is defined between the front edge and the trailing edge of the wing. A rib forming opening having an outer row aligned in the third axial direction is a rib having a rib forming opening having an outer row aligned in the second axial direction and having an outer row aligned in the third axial direction. It extends in the radial direction so as to overlap the forming opening in the axial direction. The notch is radially aligned with the outer row of ribbed openings aligned in the second axial direction. The radial height of at least one of the first axially extending passage element and the second axially extending passage element is greater than the major radial height of the axially extending passage element in the core structure. ..

The radial inner low flow framed channel element has a plurality of notches extending radially outward from the radial inner edge. Ribbing openings with inner rows aligned in the first axial direction extend radially so that the distal portion of the notch has inner rows aligned in the first axial direction. It overlaps the rib forming opening in the axial direction. A rib forming opening having an inner row aligned in the third axial direction is a rib having a rib forming opening having an inner row aligned in the second axial direction and having an inner row aligned in the third axial direction. It extends in the radial direction so as to overlap the forming opening in the axial direction. The notch of the low flow frame-shaped channel element on the inner side in the radial direction is radially aligned with the ribbed opening in the inner row aligned in the second axial direction.

In certain aspects of the core structure, each portion of the radial outer edge and the radial inner edge between the notches has a substantially flat region. In another particular aspect, the radial height H ₁ of the passage element extending in the first axial direction is greater than or equal to the radial height H _{2 of the} passage element extending in the second axial direction, where H ₂ is the major. Radial height H or more.

According to another aspect of the invention, blades in a gas turbine engine are provided. The wing has an outer wall that forms a front edge, a trailing edge, a positive pressure surface, a negative pressure surface, a radial inner end, and a radial outer tip with a tip cap. The axial direction is defined between the front edge and the trailing edge. The wing further has a trailing edge cooling circuit formed on a part of the outer wall adjacent to the trailing edge to receive cooling fluid for cooling the outer wall. The trailing edge cooling circuit has a plurality of axial passages defined by a plurality of rib structures, a plurality of radial channels, and a low flow rate frame on the outer radial side arranged adjacent to the tip cap. Has a channel. The rib structures are arranged in radial columns that are substantially lateral to the flow axis of the cooling fluid, and every other radial column rib structure is axially aligned. Forming a row. The low flow rate frame-shaped channel on the outer side in the radial direction has a plurality of protrusions extending inward in the radial direction from the tip cap. The rib structure having the outer rows aligned in the first axial direction is radial so that the distal portion of the protrusion is axially overlapped with the rib structure having the outer rows aligned in the first axial direction. It is extended to. The protrusions are radially aligned with the row rib structure aligned in the second axial direction, and the protrusions are substantially lateral to the flow axis of the cooling fluid.

In one aspect of the wing, a rib structure having an outer row aligned in a third axial direction is such that a rib structure having an outer row aligned in a second axial direction is an outer rib structure aligned in a third axial direction. It extends in the radial direction so as to overlap in the axial direction with the rib structure having the rows of. In another aspect, the radial height of the first and / or second axially extending passage is greater than the major radial height of the axially extending passage in the trailing edge cooling circuit. In some embodiments, the rib structure and protrusions are axial through a radial outer low flow frame-like channel that requires the cooling fluid to make multiple substantially 90 degree turns. The flow path is specified in.

In another aspect of the wing, the trailing edge cooling circuit is an radially inner low flow frame with multiple protrusions extending radially outward from the radial inner edge, located adjacent to the radial inner edge. It also has a radial channel. The rib structure with the inner rows aligned in the first axial direction is radial so that the distal portion of the protrusion is axially overlapped with the rib structure with the inner rows aligned in the first axial direction. It is extended to. A rib structure having an inner row aligned in the third axial direction is a rib structure having an inner row aligned in the second axial direction and a rib structure having an inner row aligned in the third axial direction. It extends in the radial direction so that it overlaps in the axial direction. The protrusions of the low flow frame-shaped channel on the inner side in the radial direction are radially aligned with the rib structure having the inner row aligned in the second axial direction, and are substantially lateral to the flow axis of the cooling fluid. The direction. In certain embodiments, the rib structure and protrusions are axially through a low radial inner low flow frame-like channel that requires the cooling fluid to make multiple substantially 90 degree turns. It defines the flow path.

The specification concludes with a claim that specifically points out the invention and explicitly claims the invention, but the invention is based on the following description relating to the accompanying drawings in which the same reference numerals represent the same elements. It is considered to be well understood.

It is a perspective view of the wing assembly according to the present invention in which a part of the outer wall is cut out to show the aspect of the present invention in detail. FIG. 1 is an enlarged side view of the section shown by Box 2A. FIG. 1 is an enlarged side view of the section shown by Box 2B in FIG. FIG. 6 is an enlarged view similar to the section shown in FIG. 2A, showing the core structure used to manufacture the wings according to the invention. FIG. 3 is an enlarged view similar to FIG. 3, showing a conventional core structure having a triple impingement trailing edge cooling configuration.

In the following detailed description of preferred embodiments, reference is made to the accompanying drawings forming a portion thereof, the drawings of particular preferred embodiments in which the invention may be practiced, but not by limitation. The morphology is shown. It should be understood that other embodiments may be used and modifications may be made without departing from the ideas and scope of the invention.

The present invention provides configurations for blades located within the turbine section of a gas turbine engine (not shown). Here, with reference to FIG. 1, a typical wing assembly 10 configured according to one aspect of the invention is shown. The wing assembly 10 has a wing 11, a platform 17, and a root portion 18. The root portion 18 is conventionally used to secure the blade assembly 10 to the shaft and disc assembly of the turbine section (not shown) and to support the blade assembly 10 in the gas flow path of the turbine section. Although aspects of the invention are described herein with particular reference to components of blade assemblies in gas turbine engines, those skilled in the art will incorporate the concepts disclosed herein in the formation of fixed vane assemblies. You will understand that can also be used.

The wing 11 shown in FIG. 1 has a front edge 12, a trailing edge 13, a negative pressure surface 20, a positive pressure surface (unsigned) opposite to the negative pressure surface 20, and a radial inner end adjacent to the platform 17. It has an outer wall forming a portion 15 and a radial outer tip portion 22. As used throughout, unless otherwise specified, "radial", "radial inside", "radial outside" and their derivatives are relative to the radial direction represented by the arrow R in FIG. It is used and its radial direction is parallel to the longitudinal axis of the wing 11. "Axial", "upstream", "downstream" and their derivatives are used with respect to the flow of combustion gas through the hot gas passages in the turbine section, where "axial" is the front and rear edges of the blade 11. It is defined between the edges 12 and 13. The wing 11 extends in the radial direction R from the inner end portion 15 in the radial direction to the outer tip portion 22 in the radial direction.

In FIG. 1, a part of the negative pressure surface 20 of the blade 11 is cut off at the radial inner end portion 15 and the radial outer tip portion 22 in order to show a part 13a of the internal structure of the trailing edge 13. The part 13a may have one or more trailing edge cooling circuits such as radial outer and radial inner trailing edge cooling circuits 14, 16, and each trailing edge cooling circuit 14, 16 respectively. , It is formed in a cavity arranged in a portion of the outer wall of the wing 11 adjacent to the trailing edge 13. Enlarged portions of the radial outer and radial trailing edge cooling circuits 14 and 16 (also referred to herein as radial outer and radial inner cooling circuits 14 and 16) are shown in FIGS. 2A and 2B. It is shown in detail in. The structure of the cooling circuit 16 on the inner side in the radial direction is substantially the same as the structure of the cooling circuit 14 on the outer side in the radial direction, and the cooling circuit 16 on the inner side in the radial direction is substantially the inversion of the cooling circuit 14 on the outer side in the radial direction. For good reason, some aspects of the invention will be described in detail only with respect to the radial outer cooling circuit 14.

With reference to FIGS. 1, 2A and 2B, the radial outer edge of the radial outer cooling circuit 14 is adjacent to the radial outer tip 22 and may be formed by the radial outer tip 22. Good. The radial outer tip 22 further includes a tip cap 24. The radial inner cooling circuit 16 is adjacent to the radial inner end 15 of the blade 11, and the radial inner edge of the radial inner cooling circuit 16 is provided by, for example, by the platform 17 as shown in FIG. 2B. It may be formed by a root portion 18 (not shown). The radial outer and radial inner cooling circuits 14 and 16 have a plurality of axial passages 28 and 28'defined by a plurality of rib structures 26 and 26', respectively, and a plurality of radial channels. It has 30, 30'and. The rib structures 26,26'may have any suitable geometry, and the rib structures 26,26' may have a substantially rectangular structure, as shown in FIGS. 2A and 2B. The rib structures 26,26'are arranged in a plurality of substantially radial columns 36, 36', which are also referred to here as ribs, and every other radial rib structure 26, 26'is arranged. 'Forms rows 38, 38' aligned in the axial direction.

The cooling fluid C _F is indicated in FIGS. 2A and 2B by arrows entering the radial outer and inner cooling circuits 14, 16 on the left or upstream side through axial passages 28, 28'. There is. The cooling fluid C _F may be received, for example, from a chord central cooling circuit (not shown) immediately upstream of the cooling fluid C _F , and the chord central cooling circuit has conventionally had a root portion 18 (see FIG. 1). ) May supply compressed air. The rib structures 26,26'are radially offset relative to each other and adjacent upstream and downstream axial passages 28, 28'. A portion of each rib structure 26,26'is axially adjacent, except for the rib structures 26,26', which form a row 38a (not labeled in FIG. 2B) aligned in the first axial direction. It overlaps with a part of the rib structures 26, 26'in the columns 36, 36'arranged in the radial direction. For example, the distal portions 44,44'of the rib structures 26,26'overlap the proximal portions 42,42' of the rib structures 26,26' in the axial direction. The distal portions 44,44'are defined as portions of the rib structures 26,26'farthest from the radial outer and inner edges of the radial outer and inner cooling circuits 14, 16 respectively. Proximal portions 42, 42'are defined as portions of the rib structures 26, 26' closest to the radial outer and inner edges.

In addition, the rib structure 26, 26 'is, passages 28, 28 extending in the axial direction' may be substantially transverse to the flow axis F _A cooling fluid C _F exiting, thereby, the cooling fluid C _F collides with 'a rib structure 26, 26' in the column 36, 36 aligned in the radial direction of the 'just downstream of the rib structure 26, 26' each of the passages 28, 28 extending in the axial direction. For example, as shown in FIGS. 2A and 2B, the axially extending lines parallel to the flow axis F _A are the proximal portions 42, 42'and the distant of every other row of rib structures 26, 26'. It intersects the ranks 44 and 44'. After colliding with the rib structures 26,26', the cooling fluid C _F is then forced to flow laterally, i.e. the cooling fluid C _F is substantially within the radially extending channels 30, 30'. It is forced to make a 90 ° turn, then turns again, flows laterally, and enters downstream axial passages 28, 28'. In other words, the rib structure 26, 26 'forms a tortuous flow path, whereby the cooling fluid C _F, the channel 30, 30 extending in the radial direction of the radially outer and inner cooling circuits 14, 16' And through the axially extending passages 28, 28', it continues to flow alternately laterally toward the trailing edge 13 of the wing 11 (see FIG. 1).

Continuing with reference to FIGS. 2A and 2B, the radial outer cooling circuit 14 has a radial outer low flow frame-like channel 34 located adjacent to the tip cap 24 and is radially inner. The cooling circuit 16 has a low flow frame-shaped channel 35 on the inner side in the radial direction arranged adjacent to the inner edge in the radial direction formed by the platform 17. The low flow frame-shaped channels 34 and 35 on the outer side in the radial direction and the inner side in the radial direction have a plurality of protrusions 40 and 40', respectively, and the protrusion 40 of the low flow rate frame-shaped channel 34 on the outer side in the radial direction has a tip. The projecting portion 40'of the low flow rate frame-shaped channel 35 extending radially inward from the radial inner surface of the portion cap 24 extends radially outward from the radial inner surface of the platform 17. At least a portion of the tip cap 24 arranged between the protrusions 40 and forming the radial outer edge of the radial outer low flow frame channel 34 may have a substantially flat region 46. .. At least a portion of the platform 17 that is located between the protrusions 40'and forms the radial inner edge of the low flow frame channel 35 that is radially inside may have a substantially flat region 46'. ..

With particular reference to the radial outer cooling circuit 14 shown in FIG. 2A, the rib structure 26 having the outer rows 38a aligned in the first axial direction may extend radially. The distal portion 44a of the overhang 40 overlaps the proximal portion 42 of the rib structure 26 with the outer rows 38a aligned axially in the first axial direction. The protrusion 40 is substantially radially aligned with the rib structure 26 having the outer rows 38b aligned in the second axial direction. The rib structure 26 having the outer rows 38c aligned in the third axial direction may also extend radially, thereby the rib structure 26 having the outer rows 38b aligned in the second axial direction. The distal portion 44 of the rib structure 26 overlaps the proximal portion 42 of the rib structure 26 having an outer row 38c aligned axially with the third axial direction.

Radial Inner Low Flow Some of the corresponding elements of the framed channel 35 are uncoded in FIG. 2B, but those skilled in the art will appreciate the features of the invention described herein in the radial inner low flow. It will be appreciated that it may be applied equally to the structure of the framed channel 35. For example, a rib structure 26'with an inner row aligned in the first axial direction extends radially so that the distal portion 44a'of the protrusion 40'is axially the first. It overlaps with the proximal portion 42'of the inner row of rib structures 26'aligned in the axial direction of 1. Similar to the structure of the low flow rate frame-shaped channel 34 on the outer side in the radial direction, the protrusion 40'of the low flow rate frame-shaped channel 35 on the inner side in the radial direction is the rib structure 26'in the inner row aligned in the second axial direction. Aligned in the radial direction. The inner row rib structure 26'aligned in the third axial direction may extend radially, thereby proximal to the inner row rib structure 26' aligned in the third axial direction. The portion 42'overlaps the distal portion 44' of the inner row rib structure 26'aligned in the second axial direction in the axial direction.

As shown in FIGS. 2A and 2B, the protrusions 40, 40'of the radial outer and inner cooling circuits 14, 16 exit from the axially extending passages 28, 28', and are radially outer and inner. It is substantially lateral to the flow axis F _A of the cooling fluid C _F passing through the low flow frame-shaped channels 34, 35. That is, a line extending parallel to the axial direction relative to the flow axis F _A, 'the distal portion 44a of the, 44a' protruding portions 40, 40 and, in the first row 38a (FIG. 2B aligned axially code It intersects with the proximal portions 42, 42'of the rib structure 26 having (not marked). The plurality of rib structures 26, 26'and the plurality of protrusions 40, 40' thereby define an axial flow path through the radial outer and inner low flow framed channels 34, 35. this flow path, a plurality cooling fluid C _F is as it flows toward the trailing edge 13 of the cooling fluid C _F flows through the radially outer and inner low flow frame-shaped channel 34 and 35 blades 11 (see FIG. 1) It is necessary to make a turn of substantially 90 degrees.

For example, as shown with reference to the radial outer cooling circuit 14 in FIG. 2A, the cooling fluid C _F indicated by the arrows was aligned with the flat region 46 of the tip cap 24 in the first axial direction. It enters the portion of the radial outer low flow frame-shaped channel 34 having the first axially extending passage 48a defined between the outer row 38a and the rib structure 26, and of the plurality of protrusions 40. Collide with one of. Similar to the flow of cooling fluid C _F through axially extending passages 28 and radially extending passages 30, the cooling fluid C _F then flows laterally, i.e., within adjacent radially extending channels 30. Forced to make a substantially 90 degree turn, then re-directed to flow laterally, for example, the rib structure 26 of the protrusion 40 and the outer row 38b aligned in the second axial direction. Enter the first axially extending passage 48b defined between and. The cooling fluid C _F then continues to flow alternately laterally towards the trailing edge 13 of the blade 11 (see FIG. 1) through the radial outer low flow framed channel 34.

As shown in FIGS. 2A and 2B, the respective distal portions 44a, 44a'of the protrusions 40, 40'in the radial outer and inner low flow frame channels 34, 35 may be completely rounded. In addition, proximal to each of the rib structures 26, 26'with axially aligned rows 38a, 38b of the first and second outer and inner low flow framed channels 34, 35 radially outer and inner. The portions 42, 42'may be completely rounded. The rounded edges prevent the onset of cracks. Otherwise, crack initiation can occur at the sharper corners of the other rectangular rib structures 26,26', as shown in FIGS. 2A and 2B.

The present invention is further described herein and is also referred to herein as a core structure for casting and forming at least a portion of the wing assembly 10, eg, shown in FIGS. 1, 2A and 2B. Includes the core. Referring to FIG. 1, the core structure includes, for example, a front edge 12, a trailing edge 13, a negative pressure surface 20, a positive pressure surface (unsigned) on the opposite side of the negative pressure surface, and a radial outer tip portion 22. It may be used to cast a gas turbine engine blade 11 having an outer wall forming a radial inner end 15. The core structure may include, for example, a ceramic core. The core structure may be used to cast and form at least a portion of the cooling configuration within the blade assembly 10. According to one aspect of the invention, the core structure may be used to form a portion 13a of the internal structure of the wing 11 adjacent to the trailing edge 13. This portion 13a, sometimes referred to herein as the trailing edge section, is one of the radial outer and radial inner cooling circuits 14, 16 or as shown in FIGS. 1, 2A and 2B. Both may be included.

The portion of the core structure shown in FIG. 3 may be used to form the radial outer trailing edge cooling circuit 14 described herein and is shown in FIG. 2A for radial outer cooling. Includes a diagram similar to the portion of circuit 14. Since the core structure for forming the radial inner cooling circuit 16 is substantially the same as the core structure for forming the radial outer cooling circuit 14, some aspects of the present invention are radial. Only the core structure used to form the outer cooling circuit 14 and the radial outer cooling circuit 14 will be described in detail. The elements of the core structure in FIG. 3 with the corresponding structures in the blade 11 and the radial outer cooling circuit 14 shown in FIGS. 1 and 2A are indicated by the corresponding reference numerals with a 1 added to the head.

As shown in FIG. 3, the core structure has radial outer cooling circuit sections 114. The radial outer cooling circuit section 114 may have a plurality of ribbed openings 126 defined by a plurality of radial channel elements 130 and axially extending aisle elements 128. The rib forming opening 126 may have any suitable geometry, and in the illustrated embodiment, the rib forming opening 126 is substantially rectangular. The rib forming openings 126 are arranged in substantially radially aligned columns 136, and every other radially aligned column 136 rib forming openings 126 form axially aligned rows 138. ing. With the exception of the rib-forming openings 126, which have rows 138a aligned in the first axial direction, the rib-forming openings 126 are radially offset with respect to each other and with respect to adjacent upstream and downstream axially extending passage elements 128. Thus, the proximal portion 142 of each rib forming opening 126, defined as the portion of each rib forming opening 126 closest to the radial outer edge 124, is in an axially aligned adjacent radial column 136. It overlaps the distal portion 144 of the rib forming opening 126. The distal portion of each ribbed opening 126 is defined as the portion farthest from the radial outer edge 124.

The radial outer cooling circuit section 114 further comprises a radial outer low flow frame-like channel element 134 located adjacent to the radial outer edge 124, which may correspond to a tip cap 24 (see FIG. 2A). .. As shown in FIG. 3, the radial outer frame-shaped channel element 134 has a plurality of notches 140 extending radially inward from the radial outer edge 124. At least a portion of the radial outer edge 124 between the notches 140 has a substantially flat region 146. The ribbing opening 126 with outer rows 138a aligned in the first axial direction may extend radially so that the distal portion 144a of the notch 140 is axially the first. It overlaps the proximal portion 142 of the ribbed opening 126 in the outer row 138a aligned axially. In addition, the notch 140 is radially aligned with the ribbed openings 126 in the outer row 138b aligned in the second axial direction. The rib forming opening 126 having the outer row 138c aligned in the third axial direction may also extend radially, whereby the rib forming opening 126 in the outer row 138b aligned in the second axial direction. The distal portion 144 of 126 overlaps the proximal portion 142 of the rib forming opening 126 having an outer row 138c aligned axially with the third axial direction.

As described above with respect to the radial outer and inner low flow frame channels 34, 35 in FIGS. 2A and 2B, as shown in FIG. 3, the distal of the notch 140 in the radial outer low flow frame channel element 134. The portion 144a may be completely rounded. In addition, the proximal portion 142 of the rib forming opening 126 having outer rows 138a, 138b aligned in the first and second axial directions may be completely rounded. In some aspects of the invention, the axial width W of the plurality of radially extending channel elements 130 may be substantially uniform along the radial range of the radially extending channel elements 130.

In another aspect of the invention, the core structure further has a radial inner cooling circuit section (not shown), eg, to define a radial inner cooling circuit 16, as shown in FIGS. 1 and 2B. You may be doing it. The radial inner cooling circuit section may typically be an inversion of the radial outer cooling circuit section 114. In particular, the radial inner cooling circuit section may have a plurality of ribbed openings defined by a plurality of radial channel elements and axially extending aisle elements. The rib-forming openings are arranged in substantially radial columns, and every other radial column of rib-forming openings forms axially aligned rows. The ribbed openings are radially offset relative to each other and to adjacent upstream and downstream axially extending aisle elements. The proximal portion of each ribbing opening overlaps the distal portion of the ribbing opening in an axially aligned radial column.

The radial inner cooling circuit section is located radially inside, for example, adjacent to the radial inner edge of the core structure forming part of the platform 17 or root 18 of the wing 11 (see FIGS. 1 and 2B). It may further have a low flow frame-like channel element. The radial inner frame channel element may have a plurality of notches extending radially outward from the radial inner edge, and the portion of the radial inner edge between the notches has a substantially flat region. .. The ribbing openings in the inner row aligned in the first axial direction extend radially so that the distal portion of the notch is axially aligned in the first axial direction. It overlaps the proximal portion of the ribbed opening with rows. The notch is radially aligned with the inner row of ribbed openings aligned in the second axial direction. Rib-forming openings with inner rows aligned in the third axial direction may also extend radially, thereby distant of rib-forming openings with inner rows aligned in the second axial direction. The position portion overlaps in the axial direction with the proximal portion of the rib forming opening having an inner row aligned in the third axial direction. Full rounding may be applied to the corresponding structure in the low flow framed channel element on the inner radial side.

The core structure for casting and forming cooling configurations within the blade assembly 10 and blade 11 shown in FIG. 1 and described herein has one or more additional core sections (not shown). These sections may further have a front edge 12, a negative pressure surface 20 and / or a positive pressure surface (not shown) of the wing 11, and an additional portion of the trailing edge 13, a radial outer tip 22. It is further noted that, and / or forming the radial inner end 15 of the wing 11 and the platform 17 and root 18 portions of the wing assembly 10. The core structure may define one or more conventional internal cooling circuits on the blade 11. For example, the core structure may have a section for defining a chord center cooling circuit, which is partially shown as chord center section 154 in FIG. 3, which section is a rib structure on the wing 11. A first radial column 136a of the rib forming structure 126 forming (not shown) is provided, which defines the inlet to the radial outer cooling circuit 14. In addition, core structure, further to enhance the cooling performed by the cooling fluid C _F flowing through the vane assembly 10 and blades 11 during operation, cooling features corresponding to the blade 11 (not shown) formed A turbulent feature, such as a trip strip 156, bumps, dimples, etc., may be defined for one or more cooling reinforcement structures.

The low flow framed channels 34, 35 according to the present invention also retain a sufficient amount of core material to ensure that the core structure has the strength required to withstand casting and to prevent unzipping of the core structure. while, to promote the efficient use of cooling fluid C _F to provide the required cooling for the airfoil 11. For comparison, FIG. 4 shows a core structure for defining a conventional radial outer trailing edge cooling circuit (not shown) with triple impingement cooling, which is shown in this figure with respect to FIG. The same reference numerals are used with a prefix of 1 to indicate the same or corresponding member. As shown in FIG. 4, the radial outer cooling circuit section 214 has a conventional frame-shaped channel element 232. The frame-shaped channel element 232 uses a tie bar and has a thicker axially continuous portion of the core structure at the radial outer edge 224 of the core structure. The downstream portion 213 of the core structure may form the trailing edge of the wing in the same manner as described for the trailing edge 13 of the wing 11 (see FIG. 1), with multiple trailing edge outlets (not shown). ) May have a plurality of trailing edge exit forming elements 258.

The thicker portion of the core structure at the radial outer edge 224 of the conventional radial outer cooling circuit section 214 shown in FIG. 4 is the core required for the core structure to withstand the casting process and prevent unzipping of the core structure. Provides strength. The conventional frame-shaped channel (not shown) resulting from the conventional frame-shaped channel element 232 shown in FIG. 4 to the conventional trailing edge cooling circuit defined by the first column 236a of the rib forming opening 226. It provides a continuous low resistance flow path for the cooling fluid directly from the inlet to the trailing edge outlet defined by the trailing edge outlet forming opening 258. In the case of the conventional triple impingement configuration shown in FIG. 4, the presence of a continuous low resistance flow path is almost acceptable. However, the use of conventional frame-shaped channel in conjunction with the highly efficient multiple impingement cooling configuration that requires to follow a cooling fluid C _F is tortuous flow paths through a conventional frame-shaped channel It produces an unacceptably large flow rate. This is because a larger percentage of the cooling fluid flow is diverted to the conventional framed channel with lower resistance and is inefficiently discharged through this conventional framed channel with lower resistance.

In contrast, the low flow frame channel elements 134 according to the invention and the resulting low flow frame channels 34,35 still retain sufficient core material to prevent unzipping of the core structure, while requiring cooling. Reduce the cooling fluid flow rate to provide. As shown in FIG. 3, the structure of the radial outer cooling circuit section 114 is a proximal portion of every other radially aligned column, i.e., second and fourth radially aligned columns 136b, 136d. Toward the radial outer edge 124 until the outermost ribbed openings 126 in the radial direction of the radial columns 136b, 136d aligned in each radial direction are continuous with the radial outer edge 124 so as to form a plurality of notches 140. Is shifting. Rib structures / rib forming openings 26, 26', 126 in axially extending rows 38, 38', 138 are radially extending, as shown in FIGS. 2A, 2B and 3 and as described herein. Extending, which helps compensate for the presence of protrusions / notches 40, 40', 140, i.e., creating axial overlap. As described herein, this radial extension and overlap ensures that the cooling fluid flow rate is sufficiently low and that the radial outer and radial inner low flow frame channels 34, the cooling fluid C _F passing through 35 is used efficiently, i.e., cooling fluid C _F passing through the radially outer and inner low flow frame-shaped channel 34 and 35, the radially outer and radially inner It ensures that it produces a turn of substantially 90 degrees, which is the same as the cooling fluid C _F passing through the winding flow path defined by the other parts of the cooling circuits 14, 16.

In addition to promoting efficient use of sufficiently produce less cooling fluid flow and the cooling fluid C _F, the low flow channel element 134 and the resulting low flow frame-shaped channel 34 and 35, particularly in the radially outer cooling Sufficient core material must also be provided to ensure structural stability during casting at the radial outer edge 124 of circuit section 114 and the radial inner edge of the radially inner cooling circuit section (not shown). .. With reference to FIGS. 2A and 3, these objectives are, in the present invention, in the radial spacing between the rib structures / rib forming openings 26,126 in the columns 36,136 aligned in each radial direction, i.e. axially. It may be reached by varying the radial height of the extending passages / passage elements 28,128.

Referring particularly to radially outer cooling circuit section 114 in FIG. 3, path elements 148a extending in a first axial direction of the radially outer low flow frame shaped inner channel element 134, 148b is the radial height H ₁ The passage element 150 having and extending in the second axial direction has a height H _{2 in the} radial direction. A major radial height H, also referred to herein as a nominal height, is indicated for a third axially extending passage element 152. The nominal or major radial height H is used to define the axially extending passages 28 present in the radial outer and radial inner cooling circuits 14 and 16 shown in FIGS. 2A and 2B. It may be defined as the minimum height of the passage element 128 extending in the axial direction. The other axially extending passage elements 128 arranged radially inside the third axially extending passage element 152 may also have a major radial height H. In a particular aspect of the invention, H ₁ may be greater than H, as shown in FIG. In some embodiments, H ₂ may be greater than H. In some embodiments of the invention, H ₁ may be H ₂ or greater, and in certain embodiments, H ₁ > H ₂ > H. In another aspect, H ₁ may be less than H ₂ . In an additional aspect of the invention, the axial widths W of the plurality of radial channel elements 130 may be substantially uniform.

Continuing with reference to FIG. 3, according to a particular example, the radial heights H ₁ , H ₂ and H may have a ratio of about 3: 2: 1 to each other. Here, H ₁ is about three times the main radial height H, and H ₂ is about twice the main radial height H. Radial columns 136 that are not aligned with the notch 140, such as the third radial column 136c shown in FIG. 3, may have a ratio of about 3: 2: 1. This is because the thickest part of the core (H ₁ or “3”), the passage element 148a extending in the first axial direction, is the radial outer edge 124 of the cooling circuit section 114 on the radial outer side and the first axial direction. This is because it is formed between the rib forming opening 126 of the row 138a aligned with the proximal portion 142. The second axially extending aisle element 150 of the third radially aligned column 136c has a thinner portion of the core (H ₂ or “2”), whereas it extends in the third axial direction. The passage element 152 has a major radial height H (“1”).

Continuing with a particular example, the radially aligned columns 136 aligned with the notch 140, such as the second axially aligned column 136b, have a ratio of about 0: 3: 2: 1. It can be seen in FIG. This is because the notch 140 extends inward in the radial direction from the outer edge 124 in the radial direction so that the portion of the core arranged radially outward from the notch 140 does not exist (“0”). The first of the second axially aligned columns 136b defined between the distal portion 144a of the notch 140 and the proximal portion 142 of the rib forming opening 126 of the first axially aligned row 138a. passage element 148b extending in the axial direction of the contrast with the thick portion of the core (H ₁ or "3"), the passage elements 150 extending in a second axial direction, a less thick portion of the core (H ₂ or The passage element 152 having "2") and extending in the third axial direction has a major radial height H ("1"). That is, as seen in FIG. 3, the adjacent radial columns 136 of the rib forming openings 126 alternate about 3: 2: 1 and 0: 3: 2 as described herein. It may have a radial spacing pattern of 1.

In some aspects of the invention, the magnitude of the axial overlap between the distal portion of the notch 140 and the proximal portion 142 of the ribbed opening 126 of the outer row 138a aligned in the first axial direction is , H ₁ may be about 25% or more. In another aspect of the invention, the magnitude of the axial overlap between the proximal portion 142 of each rib forming opening 126 and the distal portion 144 of the rib forming opening 126 in the adjacent radial alignment 136 is also. , H ₁ may be about 25% or more.

These features with respect to radial height and axial width are described for the radial outer cooling circuit section 114 as shown in FIG. 3, but those skilled in the art will describe these features herein. It will be appreciated that it is similarly applicable to the structure of the cooling circuit section inside the radial direction as it is. In addition, although described in detail with respect to the core structure, those skilled in the art may relate to radial height and axial width as shown in FIGS. 1, 2A and 2B and as described herein. These features of the present invention include passages 48a, 48b extending in the first axial direction, passages 50 extending in the second axial direction, and passages 52 extending in the third axial direction (not marked in FIG. 2b). Applicable to the corresponding axial heights of H ₁ , H ₂ and H and the corresponding axial widths of the plurality of radial channels 14 and 16 of the radial outer and inner cooling circuits 14 and 16 of the blades 11, respectively. You will understand that.

Although certain embodiments of the invention have been exemplified and described, it will be apparent to those skilled in the art that various other modifications and modifications can be made without departing from the ideas and scope of the invention. Therefore, it is intended that all such modifications and modifications within the scope of the present invention are included in the appended claims.

Claims (10)

A core structure for casting a gas turbine engine blade (11), the core structure having a trailing edge section (13a) for molding the trailing edge (13) of the gas turbine engine blade (11). However, the axial direction is defined between the front edge (12) and the trailing edge (13) of the wing (11).
At least a part of the trailing edge section (13a)
A plurality of rib-forming openings (126) defined by a plurality of radial channel elements (130) and axially extending passage elements (128), the rib-forming openings (126) being radial. The rib-forming openings (126) of every other radially aligned column (136) are arranged in a vertically aligned column (136) to form an axially aligned row (138). , Multiple rib forming openings (126),
Radial outer low-flow frame-shaped channel element (134) arranged adjacent to the radial outer edge (124) of the trailing edge section (13a) and radially inward from the radial outer edge (124). With a low flow frame-like channel element (134) on the radial outer side, with a plurality of notches (140) extending to
The rib forming opening (126) having a radial outer row (138a) aligned in the first axial direction has a distal portion (144a) of the notch (140) aligned in the first axial direction. and to overlap in axial ribs formed opening having a radially outer row (138a) (126), extending radially,
The notch (140) is radially aligned with the rib forming opening (126) in the radial outer row (138b) aligned in the second axial direction.
The radial outer row (138a) aligned in the first axial direction is arranged closest to the radial outer edge (124), and the radial outer row (138a) aligned in the second axial direction. 138b) is located second closest to the radial outer edge (124).
The axially extending passage element (128) is attached to the first axially extending passage element (148a, 148b) arranged closest to the radial outer edge (124) and the radial outer edge (124). The second closest axially extending passage element (150) and the third closest axially arranged passage element (152) to the radial outer edge (124) are Including
It said first axially extending passage elements (148a, 148b) and the radial height _H 1, _{H 2} of at least one of the second axially extending passage element (150), the core structure inside larger than half the radial height H of the third axially extending passage elements (152),
Radial height H _1, H ₂ and H is about 3: 2: 1 have a ratio to one another, H ₁ is about three times the H, H ₂ is about twice that of H ,
Core structure for casting gas turbine engine blades (11). The rib forming opening (126) having a radial outer row (138c) aligned in the third axial direction is the rib forming opening having a radial outer row (138b) aligned in the second axial direction. (126) extends radially so as to axially overlap the rib forming opening (126) having the radial outer rows (138c) aligned in the third axial direction .
The core structure according to claim 1 , wherein the radial outer row (138c) aligned in the third axial direction is arranged third closest to the radial outer edge (124) . The core according to claim 1, wherein the other axially extending passage element (128) arranged radially inside the third axially extending passage element (152) has the radial height H. Construction. The core structure of claim 1, wherein the portion of the radial outer edge (124) between the notches (140) has a substantially flat region (146). The trailing edge section further comprises a radial inner low flow frame channel element located adjacent to the radial inner edge of the trailing edge section, and the radial inner low flow frame channel element is said to be said. It has multiple notches extending radially outward from the radial inner edge,
First radially inner rows aligned in the axial direction of the rib forming openings, the distal portion of the notches, the ribs forming an opening and a shaft having a first radially inner rows aligned in the axial direction of the It extends in the radial direction so that it overlaps in the direction.
The notch is radially aligned with the rib-forming opening in a radial inner row aligned in the second axial direction of the rib-forming opening .
The radial inner row of the ribbed openings aligned in the first axial direction is located closest to the radial inner edge and is radially inner aligned in the second axial direction of the ribbed openings. The core structure according to claim 1 , wherein the row of the above is arranged second closest to the inner edge in the radial direction . The core structure of claim 5, wherein the radial inner edge portion between the notches has a substantially flat region. The blade (11) in the gas turbine engine
Radial outer tip (22) having a front edge (12), a trailing edge (13), a positive pressure surface, a negative pressure surface (20), a radial inner end (15), and a tip cap (24). ), Which is an outer wall whose axial direction is defined between the front edge (12) and the trailing edge (13).
A trailing edge cooling circuit (14, 16) formed on a part of the outer wall adjacent to the trailing edge (13) and receiving a cooling fluid for cooling the outer wall is provided. 14,16)
A plurality of axially extending passages (28,28') and a plurality of radial channels (30,30') defined by a plurality of rib structures (26,26'). (26, 26 ') are columns (36, 36 aligned in the radius direction' said rib structure is disposed), the tandem aligned with every other radial (36, 36 ') (26, A plurality of axially extending passages (28,28') and a plurality of radially extending channels (30,30'), in which 26') form an axially aligned row (38,38'). When,
Radially outer low flow frame-like channel (34) arranged adjacent to the tip cap (24) and having a plurality of protrusions (40) extending inward in the radial direction from the tip cap (24). And have
In the rib structure (26) having a radial outer row (38a) aligned in the first axial direction, the distal portion (44a) of the protrusion (40) is aligned in the first axial direction. wherein the to overlap in the axial direction rib structure (26) having a radially outer row (38a), extending radially,
The protrusion (40) is radially aligned with the rib structure (26) in a row (38b) aligned in the second axial direction.
The radial outer row (38a) aligned in the first axial direction is arranged closest to the tip cap (24), and the radial outer row (38a) aligned in the second axial direction. 38b) is arranged close to the second of the tip cap (24).
The axially extending passages (28, 28') include a first axially extending passage element (48a, 48b) arranged closest to the tip cap (24) and the tip cap (24). A second axially extending passage element (50) arranged second closest to) and a third axially extending passage element (52) third closest to the tip cap (24). Including and
Said first axially extending passage elements (48a, 48b) and the radial height _H 1, _{H 2} of at least one of said second axially extending passage element (50), said trailing edge cooling circuit (14, 16) of greater than one-half the radial height H of the third axially extending passage element (52),
Radial height H _1, H ₂ and H is about 3: 2: 1 have a ratio to one another, H ₁ is about three times the H, H ₂ is about twice that of H ,
Wings (11) in a gas turbine engine. The rib structure (26) having a radial outer row (38c) aligned in the third axial direction is a rib structure (26) having a radial outer row (38b) aligned in the second axial direction. Is extending in the radial direction so as to overlap in the axial direction with the rib structure (26) having the radial outer row (38c) aligned in the third axial direction .
The wing (11) according to claim 7, wherein the row (38c) aligned in the third axial direction is arranged closest to the third of the tip cap (24 ). The plurality of rib structures (26) and the plurality of protrusions (40) provide the radial outer low flow frame-like channel (34) that requires the cooling fluid to make a plurality of 90 degree turns. The wing (11) according to claim 7, wherein a flow path ( _CF ) is defined in the axial direction through the blade. The trailing edge cooling circuit (14, 16) is arranged adjacent to the radial inner end (15) and has a plurality of protrusions (40') extending radially outward from the radial inner edge. Further has a low flow frame-like channel (35) on the inner radial side,
Radius the rib structure with a radially inner row aligned in a first axial direction (26 '), the distal portion of the protrusion (40) (44a') is aligned with said first axial It extends in the radial direction so as to overlap with the rib structure (26') having rows inside in the direction in the axial direction.
The rib structure (26') having a radial inner row aligned in a third axial direction is the rib structure (26') having a radial inner row aligned in a second axial direction. It extends in the radial direction so as to overlap with the rib structure (26') having the inner row in the radial direction aligned in the axial direction of 3.
The radial inner row aligned in the first axial direction is arranged closest to the radial inner edge, and the radial inner row aligned in the second axial direction is the radial inner edge. The second closest arrangement, the radial inner row aligned in the third axial direction, is the third closest arrangement to the radial inner edge.
The protrusion (40 '), the rib structure (26 having a radially inner row aligned with said second axial' are aligned with) a radially claim 7, wherein the blades (11) ..

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